NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Reynolds number: 100,000 Max Cl/Cd: 31.18 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a63a108c-il-100000-n5.txt Download as CSV file: xf-a63a108c-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES 63A108 MOD C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.7233 0.08148 0.07650 0.0050 1.0000 0.0289
-8.250 -0.7289 0.07562 0.07056 0.0009 1.0000 0.0287
-8.000 -0.7323 0.06958 0.06438 -0.0025 1.0000 0.0284
-7.750 -0.7331 0.06354 0.05813 -0.0051 1.0000 0.0280
-7.500 -0.7308 0.05746 0.05174 -0.0069 1.0000 0.0276
-7.250 -0.7249 0.05142 0.04528 -0.0081 1.0000 0.0272
-7.000 -0.7145 0.04584 0.03918 -0.0086 1.0000 0.0270
-6.750 -0.6995 0.04113 0.03395 -0.0087 1.0000 0.0270
-6.500 -0.6808 0.03715 0.02941 -0.0086 1.0000 0.0273
-6.250 -0.6595 0.03371 0.02542 -0.0083 1.0000 0.0279
-6.000 -0.6362 0.03085 0.02199 -0.0081 1.0000 0.0295
-5.750 -0.6113 0.02921 0.02017 -0.0080 1.0000 0.0311
-5.500 -0.5853 0.02692 0.01743 -0.0076 1.0000 0.0323
-5.250 -0.5589 0.02502 0.01525 -0.0074 1.0000 0.0333
-5.000 -0.5323 0.02362 0.01377 -0.0072 1.0000 0.0348
-4.750 -0.5055 0.02233 0.01231 -0.0070 1.0000 0.0375
-4.500 -0.4787 0.02122 0.01113 -0.0068 1.0000 0.0403
-4.250 -0.4522 0.02006 0.00995 -0.0065 1.0000 0.0426
-4.000 -0.4255 0.01911 0.00897 -0.0063 1.0000 0.0465
-3.750 -0.3989 0.01825 0.00810 -0.0061 1.0000 0.0513
-3.500 -0.3724 0.01744 0.00731 -0.0060 1.0000 0.0572
-3.250 -0.3457 0.01668 0.00661 -0.0059 1.0000 0.0655
-3.000 -0.3188 0.01596 0.00595 -0.0058 1.0000 0.0791
-2.750 -0.2922 0.01517 0.00533 -0.0057 1.0000 0.1058
-2.500 -0.2665 0.01412 0.00479 -0.0058 1.0000 0.1917
-2.250 -0.2443 0.01256 0.00445 -0.0054 1.0000 0.4431
-2.000 -0.2233 0.01180 0.00446 -0.0036 1.0000 0.6302
-1.750 -0.2018 0.01148 0.00447 -0.0015 1.0000 0.7332
-1.500 -0.1807 0.01125 0.00446 0.0008 1.0000 0.8099
-1.250 -0.1557 0.01111 0.00448 0.0026 1.0000 0.8832
-1.000 -0.1097 0.01110 0.00447 -0.0002 1.0000 0.9576
-0.750 -0.0586 0.01109 0.00436 -0.0050 1.0000 0.9943
-0.500 -0.0347 0.01104 0.00423 -0.0049 1.0000 1.0000
-0.250 -0.0184 0.01106 0.00418 -0.0033 1.0000 1.0000
0.000 -0.0007 0.01114 0.00420 -0.0020 1.0000 1.0000
0.250 0.0449 0.01118 0.00418 -0.0058 0.9857 1.0000
0.500 0.0939 0.01120 0.00416 -0.0100 0.9632 1.0000
0.750 0.1317 0.01124 0.00417 -0.0118 0.9378 1.0000
1.000 0.1612 0.01131 0.00421 -0.0116 0.9117 1.0000
1.250 0.1862 0.01138 0.00424 -0.0105 0.8839 1.0000
1.500 0.2095 0.01144 0.00427 -0.0088 0.8542 1.0000
1.750 0.2322 0.01149 0.00427 -0.0071 0.8204 1.0000
2.000 0.2550 0.01154 0.00426 -0.0053 0.7791 1.0000
2.250 0.2775 0.01163 0.00422 -0.0033 0.7247 1.0000
2.500 0.2998 0.01182 0.00416 -0.0013 0.6479 1.0000
2.750 0.3220 0.01227 0.00412 0.0005 0.5384 1.0000
3.000 0.3460 0.01299 0.00426 0.0014 0.4175 1.0000
3.250 0.3714 0.01375 0.00454 0.0016 0.3215 1.0000
3.500 0.3977 0.01444 0.00488 0.0017 0.2560 1.0000
3.750 0.4244 0.01505 0.00525 0.0017 0.2096 1.0000
4.000 0.4511 0.01565 0.00567 0.0017 0.1755 1.0000
4.250 0.4780 0.01624 0.00616 0.0017 0.1496 1.0000
4.500 0.5047 0.01688 0.00667 0.0017 0.1299 1.0000
4.750 0.5314 0.01751 0.00724 0.0018 0.1139 1.0000
5.000 0.5580 0.01817 0.00789 0.0019 0.1009 1.0000
5.250 0.5844 0.01888 0.00857 0.0020 0.0904 1.0000
5.500 0.6106 0.01962 0.00930 0.0021 0.0817 1.0000
5.750 0.6367 0.02042 0.01011 0.0023 0.0745 1.0000
6.000 0.6625 0.02128 0.01099 0.0024 0.0684 1.0000
6.250 0.6882 0.02216 0.01186 0.0026 0.0633 1.0000
6.500 0.7138 0.02312 0.01291 0.0028 0.0586 1.0000
6.750 0.7393 0.02419 0.01411 0.0030 0.0544 1.0000
7.000 0.7643 0.02530 0.01525 0.0032 0.0514 1.0000
7.250 0.7892 0.02650 0.01662 0.0035 0.0480 1.0000
7.500 0.8136 0.02791 0.01821 0.0038 0.0454 1.0000
7.750 0.8376 0.02948 0.01998 0.0041 0.0434 1.0000
8.000 0.8607 0.03110 0.02178 0.0043 0.0415 1.0000
8.250 0.8828 0.03300 0.02403 0.0047 0.0393 1.0000
8.500 0.9049 0.03437 0.02546 0.0049 0.0380 1.0000
8.750 0.9217 0.03789 0.02965 0.0054 0.0367 1.0000
9.000 0.9362 0.04133 0.03361 0.0059 0.0357 1.0000
9.250 0.9504 0.04410 0.03670 0.0063 0.0348 1.0000
9.500 0.9660 0.04609 0.03880 0.0066 0.0339 1.0000
9.750 0.9578 0.05265 0.04618 0.0067 0.0331 1.0000
10.000 0.9422 0.05922 0.05328 0.0061 0.0327 1.0000
10.250 0.9157 0.06613 0.06054 0.0044 0.0327 1.0000
10.500 0.8826 0.07484 0.06944 -0.0016 0.0332 1.0000
10.750 0.8515 0.08869 0.08337 -0.0135 0.0338 1.0000
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Polar data table (+)
Polar graphs
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